单晶涡轮叶片典型任务循环蠕变分析  

Creep analysis of single crystal turbine blade under typical mission cycle

作　　者：石多奇[1] 张雨曼 隋天校 杨晓光[1] SHI Duoqi;ZHANG Yuman;SUI Tianxiao;YANG Xiaoguang(School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2024年第6期1-9,共9页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅳ-0012-0049)。

摘　　要：针对单晶涡轮叶片在发动机典型任务循环下的多工况蠕变计算问题,结合变载条件下的单晶合金蠕变本构模型,开发了用于高温结构蠕变计算的ABAQUS/UMAT用户子程序。对某型单晶涡轮叶片进行了典型任务循环下的蠕变计算,识别出可忽略蠕变损伤的工作状态从而实现了载荷谱简化,分别计算了该涡轮叶片在10000个战斗机飞行循环和40000个运输机飞行循环下的蠕变变形,并进行了蠕变寿命评估。结果显示:计算采用的典型载荷状态中,该叶片在巡航及以下状态产生的损伤较小,进行蠕变计算时可以删除,简化后的蠕变载荷谱与原载荷谱下叶片产生的蠕变变形基本相等;不同飞机任务剖面下涡轮叶片具有不同的蠕变寿命,在采用的战斗机典型飞行循环下,该叶片的蠕变寿命约为运输机飞行循环下的1/14,这与发动机的大功率状态持续时间占比有关。Considering the multiple working conditions creep calculation of single crystal turbine blade under the typical mission profile of engine,combined with the creep constitutive model of single crystal super-alloy under varying loading,a ABAQUS/UMAT subroutine for creep calculation of high temperature structure was developed.The creep of a single crystal turbine blade under the typical design load spectrum was calculated,and the working state of negligible creep damage was identified,so as to simplify the load spectrum.The creep deformations of the turbine blade under 10000 mission cycles of fighter and 40000 mission cycles of transport aircraft were calculated respectively,and the service life was evaluated.The results showed that,under the typical load states used in the calculation,the creep damage of turbine blade under engine cruise state and below was small,which can be ignored in creep calculation.The creep deformation of turbine blade under the simplified creep load spectrum was basically equal to that under the original load spectrum;turbine blades had different creep life under different aircraft mission profiles.Under the typical mission cycle of fighter used in the calculation,the creep life of the turbine blade was about 1/14 of that of transport aircraft,which was related to the duration of high-power state of the engine.

关 键 词：涡轮叶片 典型任务循环 蠕变变形 寿命评估 变载蠕变模型 UMAT子程序 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]